Power conversion machine



Jan 11, 1955 G.'J. HUEBNER, JR., ETAL POWER CONVERSION MACHINE FiledDSC. 2, 1949 WEL/Al /777'aFA/EKS,

United States Patent O 2,699,319 POWER CONVERSION MACHINE George J.Huebner, Jr., Bloomfield Hills, and David M. Borden9 Huntington Woods,Mich., assignors to Chrysler Corporation, Highland Park, Mich., acorporation of Delaware Application December 2, 1949, Serial No. 130,7324 Claims. (Cl. 253-69) The present invention relates to compressors,pumps, turbines and similar bladed, rotary power conversion machinesutilizing compressible fluids for powering the same. More particularly,this invention relates to a means for controlling the direction of iiowof the compressible fluids through concentric bladed stages of themachine to obtain optimum performance thereof.

It is known that the effect of the working gases upon the blading forsuch power conversion machines may be altered by providing a means forindividually pivoting the blades as desired about an axis extendinglengthwise of the blades. A suitable locking means may be provided forsuch pivoted blades for fixing the same at some desired blade angle.However, such constructions are usually accompanied by serious designdifliculties which have no practical solution. The lack of uniformity ofthe movement of the blades about their pivots, erosion and thedifliculty in mounting a pivoted blade assembly upon a rotor componenthave prevented such pivoted blade machines from obtaining widespreadacceptance.

According to a feature of the present invention a relatively simple anduniform blading arrangement is provided by which different bladingeffects may be achieved merely by adjustably controlling appropriateportions of the blading system.

According to a further feature of the invention, means are provided forchanging the power rating and operating characteristics of the machineas desired for a specilied motive liuid ow or shaft torque. Portions ofthis means are disposed within the blading of the machine.

According to still a further feature of the invention a nozzle sectionis provided which has a plurality of effective discharge angles madepossible by causing auxiliary blade sets therein to freewheel or to befixed in a stationary position.

According to another feature of the invention a rotor section having aplurality of effective blade angles is provided for selectivelyachieving different degrees of energy interchange between the rotor andthe motive fluid, all other conditions being the same.

According to still another feature, relatively rotative parts areprovided of which the relative movement one to the other is readilycontrolled and positively and uniformly changed to suit variousconditions.

According to yet another feature a releasable machine part is providedwhich, when not needed to ac commodate the change in some externaloperating factor of the machine, may be allowed to yield and free wheelwithout substantial effect on the machine.

Various other features and objects and advantages will become apparentfrom the following detailed description and the accompanying drawingthrough which the invention is illustrated by way of example and inwhich:

Figure 1 is a longitudinal view in section of' a machine to which theinstant invention has been applied;

Figure 2 is a section through the blading of the machine of Figure 1;

Figure 3 is an enlarged diagrammatic view of the blading of Figure 2;

Figure 4 is a modified form of blading; and

Figure 5 illustrates a further modification of the blad- 1n gIn regardto Figures l and 2 particularly, a turbine selected as illustrative ofan application of the present invention is shown and it includes outerand inner walls and 12 defining an annular passage for accommodating theow of compressible energy fluids.

Engaging walls 10 and 12 are flanges 15 and 16. Flange 5 1s carried by aWall 18 in which is received the tip portions of a plurality of nozzlevanes or blades in the nozzle section of the turbine. A rib 22 formed onthe wall 18 is joined to an end wall 24 for the turbine. The base ofeach vane 20 is mounted to a stationary carrier portion 26 which may beprovided with inwardly directed lugs as shown at 28.

Other blading 30 is also disposed in the nozzle section, the tip 32 ofwhich is positioned close to wall 18 but in a non-contacting relationtherewith. The base 34 of blade 30 is mounted in a carrier portion 36.Outer wall 18 is provided with a radially extending flange 3S whichmarks the end of the nozzle section of the turbine and mates with acompanion flange 39.

The rotor section of the turbine beginning at flange 39 contains a rotorblade 40, the tip 42 of which is disposed adjacent to wall 44 of theturbine outer housing but in non-contacting relation therewith. The baseof blade is shown at 46 mounted in a carrier portion 48, the rotorsection additionally having another blade which is adapted to rotatewithin and in spaced relationship with wall 44. A flange 52 provided onwall 44 and a mating flange 54 join to connect an outer wall 56 inregistry with the gas passage. Inner wall 58 cooperates with wall 56 toconfine the gases to a selected path. Blade 50 is carried by a carrierportion 60 which is rotatably mounted adjacent to wall 58. lt is to benoted that a slight clearance is provided between the aforesaid carrierportions and between each carrier portion and the wall 98 to provide ameans for obtaining a controlled leakage into the combustion gas path ina fashion more fully described later.

An end wall 64 of the turbine has a portion 62 forming a gastightconnection with wall 58 and a reinforcing bracket is provided for theend wall at 66. At the forward end of the turbine is a wall 68 providedwith a radial rib 70 and peripheral flange 72. Flange '/"2 is connectedwith lug 28 by means of a fastener 74. A fastener 76 on wall 68 servesto secure its inner margin to a lug 78 formed on the main casing 80 ofthe turbine. Oil fitting 82 is threadably received in casing S0 andcornmunicates through passage 34 and branch 86 with an oil chamber 88.Oil chamber 88 serves to lubricate a bearing 90, the inner race of whichis retained in place in casing by a ring segment 92. The outer race ofbearing 90 is held in position by a similar ring segment 94 in a hub 96rotatably mounted on bearing 90. Engageable parts 98 and 100 are formedin association adjacent hub to provide a brake for the hub. An opening103 formed in the wall of casing 80 receives an automatically controlledor operator-controlled member 102 which may be utilized to causeengagement between braking parts 98 and 100 and which may be op eratedby a shifter yoke lever generally indicated at 101. A sealing ring 104is provided between casing 80 and the hub 96 rotatably mounted thereinfor the purpose of conning the oil to passages devoted to lubrication.

An opening 108 is provided in casing 80 for the introduction of air orother coolant which may be under suitable pressure and led into achamber defined by end wall 68 and the web 110 of the wheel mounted onhub 96. The entering coolant may pass along a rib 112 formed on web andinto the compressible combustion gas passage by the controlled leakmentioned and may also pass through a communication 114 formed in web110. Hub 96 has a closing plate 116 in attachment adjacent bearing 90.

Disposed along axis 117 of the turbine is main shaft 113 journalled inoutboard bearings 120 and 122 which latter are firmly held in casingportion 124. The inner end 126 of the main shaft is secured to a hub 128of a wheel 130, Coolant which passes through described pas' sage 114rnay enter the chamber between web 110 and wheel 130 and pass therealonginto the motive gas passage. Coolant may also pass through an opening132 formed in wheel 13d and enter into a chamber between wheel 13@ andanother wheel 134. Blades itl and 50 are mounted for rotation with theserespective wheels.

An opening 136 formed in wheel 134 allows passage of coolant into thechamber between end wall 64 and wheel 134. Wheel 134 has a hub 138firmly secured as by splines to a shaft 140 coaxial with and surroundingmain shaft 118. A seal 142 for the coolant, which may be of thelabyrinth type, cooperates with an end of shaft 140 to confine thecoolant within end Wall 64 and is provided with a connection at 144sealing it to end wall Intermediate coaxial shafts 118 and 140 isdisposed a pair of pilot bearings 146 and 148. Mounted in turn inbearings 150 and 152, the shaft 140 is effectively supported in portion154 of the turbine casing. Forme on shaft 118 is a guide member 156formed with a guide opening 157. Adjacent this guide opening aredisposed engageable parts 158 and 160 which constitute a clutch. Themember 160 of the clutch is operated to eiect engagement between theclutch parts by an operator-controlled member 162 which may in turn beoperated by a shifter yoke lever generally indicated at 163.

As to operation of the construction shown in Figures 1 and 2, let it beassumed that braking parts 98 and 100 are mutually engaged, and thatclutching parts 158 and 160 are mutually engaged. Therefore, thecompressible energy gases will be passed along the passage 14 and uponintroduction into the nozzle section will be deected so as to acquiretangential velocity. This tangential velocity becomes manifest upon thegases entering the rotor section of the turbine, and by virtue of theirdeection and the change in tangential velocity in passing along blades40 and 50 will apply force to the blades of the rotor section therebytending to rotate them in a clockwise direction as when viewed from anupstream position. When engageable parts 98 and 100 are released, thetorque reaction on blades 30 is no longer exerted on the casingtherethrough and instead of serving effectively in their nozzle vanecapacity these blades 30 and the associated wheel assembly will rotatefreely upon bearing 90 in a direction opposite to rotor rotation, or inother words, counterclockwise. As a result, the tangential velocity ofthe energy gases in passing through the nozzle section will be reducedand blades 30 will offer substantially no interference with the turbineprocesses. Regardless of the particular tangential velocity of thc gaseson entering the rotor section the gases will tend to be turned whiletransferring their energy to blades 40 and will lose some of theirtangential velocity. lf clutching parts 158 and 160 are disengaged theblades 50 will tend to freewheel in their bearings 150, 152, 146, and148 and will not interfere to any appreciable extent with the turbineprocesses.

Reference may be had to Figure 3 for a more complete understanding ofthe operating principles applicable to the above discussion. It will beobserved that widths wz and W4 between blades are less than either Widthw1 or w3. Blades 20 may be considered xedly mounted in the turbinecasing in a disposition such that their zero lift line 21 is at an angleof lift L1 to the axis 117 of the machine. With respect to the row ofblades 20, the individual blades are of a height h1, and the distancebetween them as respects the included passage is of width w1. Whilepassing through blades 20, the compressible gases must pass through apassage of the dimensions h1, w1 and submit to a turning effect in aclockwise sense in accordance with the angle of lift L1. The machinedescribed being of a single pass, single-stage axial flow type, theinward velocity v1 to blades 20 in vector form is parallel to the axis117 of the machine and the exit velocity of the gases may be representedby a vector vz making an angle p2 thus producing a tangential velocitycomponent vt.

If blades 30 are allowed to rotate freely in the casing, then the gaseswould enter the rotor section of the machine with a velocity v2 and atan angle Q52. Blading 30 is effectively disposed in the machine so thatthe Zero lift line 31 effects an angle of lift L2 with the axis 117 ofthe machine. Angle L2 exceeds the previously considered angle of lift L1of blades 20 and hence when blades 30 are held against movement anadditional turning effect is given the motive fluid. Owing to theincreased angularity of blades 30, the width wz of the passage definedtherebetween is narrower than the width wi previously considered andinasmuch as the heights h1, h2 of respective blades 20 and 30 are nearlythe same, the passage dened by blades 30 is of a more restrictedcharacter than the passages defined by blades 20. As a result of holdingblades 30 against rotation, the velocity vector of its discharging gaseswill be of the order of vector v3 having a greater angle 3 to the axisof the machine than angle qbz just considered and the tangentialvelocity vt of vector v3 will also be in excess of the tangentialcomponent vr of velocity v2. The compressible energy gases are thereforesubjected to an additional turning effect in a clockwise sense.

When blading 40 and 50 is held nized rotation, the bucket speed mayvalue u. Blading 40 is effectively disposed in the machine such that itszero lift line 41 is at an angle L3 with the axis of the machine. Theenergy gases are introduced into blading 40 and as they are turnedthereby in a counterclockwise sense in passing along the passage ofdimensions ha, w3 they deliect and accordingly impart energy to blading40. The tangential velocity component vr of the velocity v4 of the gasesdischarged from blading 40 is of lesser magnitude than the velocitycomponent in the tangential direction of the entering gases and theangle gbr made by vector velocity v4 is of lesser magnitude than anglep3 made by the entering iiuid. The lift angle L3 is of an opposite senseto lift angle L2. In the event that blading 50 is allowed to freewheel,the gases will leave the rotor section with a velocity having amagnitude and direction substantially the same as velocity v4 and anglep4 respectively. That is, the net change will be a turning in acounterclockwise sense as produced solely by blading 40. It will benoted, however, that blading 50 is effectively set in the machine suchthat its zero lift line 51 makes an angle L4, relative to the axis ofthe machine, which is greater than angle L3 but of the same sense.Passages W4 of blading 50 are narrower in magnitude than w3, the widthof the passages of blading V40, and since the height of these blades,that is h3 and h4, is of the same order, a more restricted iiow mustpass through blades S0. Further turning of the energy tiuid results in acounterclockwise whirl sense and the exit velocity v5 of the tiuids maybe reduced in angularity to a small value s lying on either side of theaxis of the machine and of relatively minor tangential component vr.Situations are readily conceivable in which it would be desirable toallow blades 30 and 50 both to freewheel, both to be held againstrotation to its complernentary member 20 or 40, or either allowed tofreewheel as the other is held against such unrestrained rotation.

In the modification of Figure 4 is shown a section through the bladingof a turbine having only one set of blading 220 in the nozzle sectionand two sets of blading 240 and 250 in the rotor section. The effect ofblades 220 is much the same as the elfect which would be obtained ifboth sets of blades in the nozzle section of the first embodiment werepermanently locked together. Rotor blading 240 and its auxiliarycomponent 250 are arranged either for independent rotation, one on themain shaft and one freewheeling, or for synchronized rotation as in theirst embodiment wherein they are indexed together.

In the modification of Figure 5, a turbine appears which has a nozzlesection comprising blades 320 and blades 330. One or the other of thesegroups of blades is permanently held in the turbine casing, and theother is either held against rotation or allowed to freewheel asdesired. The rotor section of the embodiment of Figure 5 is composed ofa row of single blades 340 which have much the same effect in operationas a conventional turbine or much the same operation as the firstembodiment if the engageable parts 158 and 160 thereof were permanentlylocked together.

It will be apparent that though the blading effect in the machine abovedescribed may be varied through use of automatically controlled oroperator-controlled parts, still, non-uniformity in blade lift anglescannot result as between blades of the same row since blades of the samerow do not have to be adjusted relative to one another. The freewheelingsets are either effectively in use or not in use and the blade anglesare not physically changed at all but rather are merely changed as totheir eiectiveness for the particular ends and purposes sought.

While the invention has been described with respect to certain preferredexamples selected to give satisfactory results, it will be understood bythose skilled in the art, after understanding the invention, thatvarious changes and modifications may be made without departing from thespirit and scope of the invention.

together for synchrobe of the designated What is claimed is: 1. A singlepass axial flow fluid turbine comprising a casing, a pair of concentricshafts supported by a portion of said casing and journalled one withinanother for relative rotation, a vvheel hub including a third bladearranged in series in that order behind said fluid nozzle vane, therespective wheel means being carried by said Wheel hub member, by oneshaft of said pair of shafts, and by the other shaft of said pair ofshafts, said first blade being curved and set for an angle of liftgreater than said predetermined angle of lift of the nozzle vane, saidsecond blade being curved and set for a preselected angle of liftrelative to the axes of said shafts and said third blade being curvedand set for an angle of lift greater than said preselected angle of liftof the second blade, brake portions connected to said wheel hub memberand said other casing portion and engageable to hold the wheel hubmember and the Wheel means including the first blade against rotationfor increasing the tangential velocity of the fluid leaving the nozzlevane, and a clutch portion connected to each of said shafts andengageable to lock the shafts and the second and third blades and theirrespective associated wheel means for rotation together whereby thesecond blade decreases the tangential velocity of the passing uid andderives energy therefrom and the third blade further decreases thetangential velocity of the passing fluid and derives further energytherefrom.

2. A single pass axial flow fluid turbine comprising a casing, a pair ofconcentric shafts supported by a portion of said casing and journalledone within another for relative rotation, a vvheel hub to each of saidshafts, a fixed fluid nozzle including a vane curved and set at apredetermined angle of lift relative to the axes of said shafts, saidbearing means and said Xed fluid nozzle being supported by anotherportion of said casing, wheel means including a first blade and wheelmeans including a second blade and Wheel means including a third bladearranged in series in that order behind said shafts and frictionallyengageable to lock the shafts and the second and third blades and theirrespective associated Wheel means for rotation together whereby thesecond blade decreases the tangential velocity of the passing fluid andderives energy therefrom and the third blade further decreases thetangential velocity of the passing fluid and derives further energytherefrom.

3. A single pass axial flow fluid turbine comprising a casing, a p airof concentric shafts supported by a portion porting said hub member forindependent rotation relative to each of said shafts, a fixed uid nozzleincluding a vane curved and set at a predetermined angle of liftrelative to the axes of said shafts, said bearing means and said fixedfluid nozzle being supported by another portion of said casing, wheelmeans including a first blade shaft of said pair of shafts, and by theother shaft of said first blade being curved and set for an angle oflift greater than said predetermined angle of lift of the nozzle vane,said second blade being curved and set for a preselected angle of lift1n an opposite sense to said predetermined angle relative to the axes ofsaid shafts and said third blade being curved and set for an angle oflift greater than said preselected angle of lift of the second blade,brake portions connected to said wheel hub member and said other casingportion and engageable to hold the wheel hub member and a clutch portionconnected to each of said shafts and engageable to lock the shafts andthe second and third energy therefrom.

4. A single pass axial flow fluid turbine comprising a casing, a pair ofconcentric shafts supported by a portion of said casing and journalledone Within another for relative rotation, member coaxially disposed withrespect to said pair of shafts bearing means for supporting said hubmember for independent rotation relative to each of said shafts, a fixedfluid nozzle including a vane curved and set at a predetermined angle oflift relative carried by said Wheel hub member, by one shaft of saidpair of shafts, and by the other shaft of said pair of shafts,

of lift greater than said preselected angle of lift of the second blade,a turbine housing member adjacent the bearing means contained in saidwheel hub member secured to said other casing portion and being adaptedto contain pressurized cooling air for the Wheel means, brake portionsconnected to said wheel hub member and said other casing portion andengageable to hold the wheel hub member and the wheel means includingthe first blade against rotation for increasing the tangential nozzlevane, and a clutch therefrom, there being a slight clearance providedbetween said wheel means each with respect to the other and with respectto the housing member so as to provide a path for the controlled leakageof said coollng air into the path of said fluid as it passes saidblades.

References Cited in the tile of this patent UNITED STATES PATENTS

